Steady and unsteady heat transfer in a transonic film cooled turbine cascade, ASME 99-GT-259 PDF Download
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Author: O. Popp
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Category :
Languages : en
Pages : 0
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Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Indianapolis, Indiana, June 7-June 10, 1999.
Author: O. Popp
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Category :
Languages : en
Pages : 0
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Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Indianapolis, Indiana, June 7-June 10, 1999.
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Category :
Languages : en
Pages : 0
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The unsteady interaction of shock waves emerging from the trailing edge of modern turbine nozzle guide vanes and impinging on downstream rotor blades is modeled in a linear cascade. The Reynolds number based on blade chord and exit conditions (5 x 10(exp 6) and the exit Mach number (1.2) are representative of modern engine operating conditions. The relative motion of shocks and blades is simulated by sending a shock wave along of stationary shock waves. The blade geometry is a generic version of modern high turning rotor blade with transonic exit conditions. The blade is equipped with a showerhead film cooling scheme.
Author:
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Category : Mechanical engineering
Languages : en
Pages : 484
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Author: Thomas Beutner
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Category : Turbomachines
Languages : en
Pages : 300
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Author:
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Category : Mechanical engineering
Languages : en
Pages : 492
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Author: Wolfgang Ganzert
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Category :
Languages : en
Pages : 0
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Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Indianapolis, Indiana, June 7-June 10, 1999.
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Category : Aeronautics
Languages : en
Pages : 934
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Author:
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Category :
Languages : en
Pages : 0
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An experimental program was performed to study the effects of high strength shocks on the film cooling heat transfer in a transonic turbine blade. Shocks stronger than seen in actual engines were generated by a shock tube and directed to pass into the cascade upstream of a linear set of blades. The results indicate that the increased strength of the shocks do not disrupt the boundary layer on the blade. Therefore, the heat transfer is still predictable by the methods determined for lower strength shocks, as reported in the attached two papers (presented in Munich during this research program). As a transition to work on high free-stream turbulence effects, initial results for a blown grid were obtained in low speed flow. The corresponding report is attached, but has not yet been published.
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Category : Airplanes
Languages : en
Pages : 580
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 492
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